Environmental control system pack pallets

ABSTRACT

An Environmental Control System (ECS) includes a pallet which supports at least one ECS component. The pallet defines a pallet surface that matches an aircraft outer mold line.

BACKGROUND

The present invention relates to an aircraft environmental controlsystem, and more particularly to a palletized arrangement therefor.

Aircraft typically include an environmental control system (ECS) withredundant air-conditioning ECS packs. The ECS packs provide essentiallydry, sterile, and dust free conditioned air to the cabin at the propertemperature, flow rate, and pressure to satisfy pressurization andtemperature control requirements.

The ECS packs are typically located under the wing at the center of theaircraft. Hinged access panels form the Outer Mold Line (OML) of theaircraft and provide access to the ECS pack. Although effective, thistype of conventional pack mount arrangement may limit pack access fromonly one direction—upward from beneath the wing.

SUMMARY

An Environmental Control System (ECS) pack according to an exemplaryaspect of the present invention includes at least one ECS component; anda pallet which supports the at least one ECS component, the palletdefines a pallet surface that matches an aircraft outer mold line.

An aircraft according to an exemplary aspect of the present inventionincludes a pallet which supports an ECS pack, the pallet mountable to afirst spar and a second spar to enclose a bay. The pallet defines apallet surface that matches an aircraft outer mold line.

A method of mounting an Environmental Control System (ECS) Pack to anaircraft according to an exemplary aspect of the present inventionincludes mounting at least one ECS component to a pallet; and installingthe pallet to an aircraft such that a pallet surface matches an aircraftouter mold line.

BRIEF DESCRIPTION OF THE DRAWINGS

The various features and advantages of this invention will becomeapparent to those skilled in the art from the following detaileddescription of the disclosed non-limiting embodiment. The drawings thataccompany the detailed description can be briefly described as follows:

FIG. 1 is a general perspective view of one exemplary aircraftembodiment for use with the present invention;

FIG. 2 is an expanded view of two ECS packs mounted within a wing boxinterface area;

FIG. 3 is an exploded view of one ECS pack; and

FIG. 4 is a schematic top view of one ECS pack.

DETAILED DESCRIPTION OF THE EXEMPLARY EMBODIMENTS

FIG. 1 schematically illustrates an aircraft 10 having a wing 12 whichattaches to a fuselage 14 in a wing box interface area 16 between thefuselage 14 and wing 12. The wing 12 typically supports two or moreengines 18. Although a particular aircraft configuration is illustratedin the disclosed embodiment, other aircraft types will also benefit fromthe present invention.

An Environmental Control System (ECS) 20 typically includes a multipleof various ECS components 23 such as, for example only, a vapor cyclesystem, turbocompressors, regulating valves, heat exchangers, and othercomponents which are packaged relatively close together to define an ECSpack 22 (FIG. 2). The ECS components 23 of the ECS pack 22 provides anair cycle refrigeration system that utilizes ambient RAM air as arefrigerant though a combined turbine and compressor machine—commonlyreferred to as an air cycle machine (ACMS) 24 (illustratedschematically). The ACMS 24 may be powered by the same bleed that isconditioned for cabin air and which is usually supplied by the gasturbine engines 18 which provide aircraft propulsion. Alternatively,cabin air compressors may be utilized and located within the ECS pack22. The ECS pack 22 may alternatively or additionally be powered byauxiliary power units (APUs) that are separate gas turbine engines whichdo not provide propulsion but may in part power the ECS packs as well asother aircraft equipment. The ECS pack 22 is often located in the wingbox interface area 16.

Referring to FIG. 3, a pallet 26 supports and mounts ECS components 23of the ECS pack 22. The pallet 26 provides the framework and supportstructure for the ECS components 23 (FIG. 2) mounted thereto as well asdefines an outer skin surface of the aircraft 10. The palletizedarrangement of the ECS pack 22 facilitates ECS pack pre-assembly andtest as an integrated unit which minimizes air framer labor andinstallation time during aircraft assembly.

The pallet 26 generally includes a framework 26F and a pallet lowersurface 26L that matches the aircraft outer mold line (OML) in the wingbox interface area 16. That is, the pallet lower surface 26L operates asan integrated fairing which defines an outer skin of the aircraft 10such that when the ECS pack 22 is mounted within an ECS bay 10B of theaircraft 10, the pallet lower surface 26L matches the aircraft OML (FIG.1). It should be understood that various surface contours whichcorrespond to the aircraft OML may be utilized herewith and the pallet26 should not be limited to the disclosed wing-box area 16 as otheraircraft positions may be defined by the pallet lower surface 26L.

The pallet lower surface 26L may include one or more access panels 26Awhich facilitate final connection and adjustments where required whenthe ECS pack 22 is attached to the aircraft 10. That is, the accesspanels 26A may be relatively small, removable panels which are locatedat particular areas of the pallet 26 for particular functions.

The pallet 26 includes a multiple of mount points 28 (FIG. 4) whichprovide attachment to the aircraft 10. The mount points 28 may attachdirectly to a front spar 16A, a rear spar 16B and a keel beam 16C withinthe wing box interface area 16 such that no attachments need be provideddirectly to the wing and/or a center fuel tank typically containedtherein as well as minimization or elimination of conventional end sheetmounts and tie rods.

The ECS pack 22 may be lowered for servicing to provide five (5) surfaceaccess (top and each of four side) to provide significant access to theECS components 23. The increased accessibility facilitates a higherpackage density which results in a smaller required volume as well asincreased access to other aircraft systems routed through the wing boxinterface area 16 when the ECS pack 22 is removed.

Various systems and methods may be utilized to raise and lower thepallet 26 such as, for example, a fish pole hoist or lift truck. Themount points 28 may alternatively include integral hoists 30 or the liketo raise and lower the pallet 26. The mount points 28 may alternativelyinclude a hinge system to facilitate access to the ECS pack 22. Thepallet lower surface 26L may also include one or more access panels 26Awhich facilitate final connection and adjustments where required whenthe ECS pack 22 is attached to the aircraft 10. That is, the accesspanels 26A may be relatively small, removable panels which are locatedat particular areas of the pallet 26 for particular functions.

The ECS pack 22 also facilitates usage of a single insulation blanket 32over all of the ECS components 23. That is, the blanket 32 replaces amultiple of individual blankets in which each blanket covers anindividual ECS component.

Referring to FIG. 4, the ECS pack 22 may include various integrationfeatures such as guide pins 34 to position the pallet 26, a RAM inletheader 36, a RAM outlet header 38, flow ducts 40, wire harnessconnections 42, and current Return Network (CRN) connections 44 whichfacilitate interface with the aircraft 10. It should be understood thatvarious other interfaces may alternatively or additionally be provideincluding, for example only, picture frame mounted heat exchangers.

It should be understood that relative positional terms such as“forward,” “aft,” “upper,” “lower,” “above,” “below,” and the like arewith reference to the normal operational attitude of the vehicle andshould not be considered otherwise limiting.

It should be understood that like reference numerals identifycorresponding or similar elements throughout the several drawings. Itshould also be understood that although a particular componentarrangement is disclosed in the illustrated embodiment, otherarrangements will benefit from the instant invention.

Although particular step sequences are shown, described, and claimed, itshould be understood that steps may be performed in any order, separatedor combined unless otherwise indicated and will still benefit from thepresent invention.

The foregoing description is exemplary rather than defined by thelimitations within. Many modifications and variations of the presentinvention are possible in light of the above teachings. The disclosedembodiments of this invention have been disclosed, however, one ofordinary skill in the art would recognize that certain modificationswould come within the scope of this invention. It is, therefore, to beunderstood that within the scope of the appended claims, the inventionmay be practiced otherwise than as specifically described. For thatreason the following claims should be studied to determine the truescope and content of this invention.

What is claimed is:
 1. A Environmental Control System (ECS) packcomprising: an Environmental Control System (ECS) pack comprising amultiple of ECS components; and a pallet which supports said multiple ofECS components, said pallet defines a pallet surface that matches anaircraft outer mold line; wherein said pallet is mountable within a wingbox interface area of an aircraft.
 2. The ECS pack as recited in claim1, wherein said multiple of ECS components includes an Air CycleMachine.
 3. The ECS pack as recited in claim 1, wherein said palletdefines a multiple of mount points.
 4. The ECS pack as recited in claim1, wherein said pallet defines at least one access panel though saidpallet surface.
 5. The ECS pack as recited in claim 1, furthercomprising a single insulation blanket to cover said multiple of ECScomponents.
 6. The ECS pack as recited in claim 1, wherein said palletdefines a multiple of guide pins.
 7. The ECS pack as recited in claim 1,wherein said pallet defines a RAM inlet header.
 8. The ECS pack asrecited in claim 1, wherein said pallet defines a RAM outlet header. 9.The ECS pack as recited in claim 1, wherein said pallet defines at leastone flow duct.
 10. An aircraft comprising: a first spar; a second spar;a keel beam connected to said first spar and said second spar to atleast partially define a bay; an Environmental Control System (ECS) packcomprising at least one ECS component installable within said bay; and apallet which supports said ECS pack, said pallet mountable to said firstspar and said second spar to enclose said bay, said pallet defines apallet surface that matches an aircraft outer mold line.
 11. Theaircraft as recited in claim 10, wherein said bay is defined in a wingbox interface area of said aircraft.
 12. The aircraft as recited inclaim 11, wherein said pallet surface comprises a pallet lower surfacethat matches said aircraft outer mold line of said wing box interfacearea.
 13. The aircraft as recited in claim 11, wherein said palletsurface operates as a fairing that defines at least in part an outerskin of said aircraft.
 14. A method of mounting an Environmental ControlSystem (ECS) Pack to an aircraft comprising: mounting a multiple of ECScomponents to a pallet; and installing the pallet to an aircraft suchthat a pallet surface matches an aircraft outer mold line; wherein saidpallet is mountable within a wing box interface area of an aircraft. 15.A method as recited in claim 14, further comprising utilizing saidpallet to provide an interface between the at least one ECS componentand the aircraft.
 16. A method as recited in claim 14, furthercomprising accessing the at least one ECS component through an accesspanel through the pallet surface.
 17. A method as recited in claim 14,further comprising covering the multiple of ECS components with a singleinsulation blanket.